Airworthiness Directive

Hide details for Federal Register InformationFederal Register Information
This information is not available.



Hide details for Header InformationHeader Information
DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

Amendment 39-1433; AD 72-08-06



Airworthiness Directives; Piper Models PA 28-140, PA 28-150, PA-28-160, PA-28-180, PA-28-235, PA 32-260, and PA-32-300 Airplanes
PDF Copy (If Available):


Hide details for Preamble InformationPreamble Information
AGENCY: Federal Aviation Administration, DOT





DATES: Effective April 14, 1972.






Hide details for Regulatory InformationRegulatory Information

72-08-06 PIPER: Amendment 39-1433. Applies to Model PA 28-140 airplanes, Serial Numbers 28-20000 and up; Model PA 28-150/-160/-180 airplanes, Serial Numbers 28-01 and up; Model PA 28-235 airplanes, Serial Numbers 28-10000 and up; Model PA 32-260 airplanes, Serial Numbers 32-01 and up; and Model PA 32-300 airplanes, Serial Numbers 32-40000 and up. Serial Numbers prefixed by model year, such as 28-7120000 are included in effectivity.

For airplanes having main landing gear torque links, P/N 65691-00 or P/N 65691-00V, compliance required within the next 50 hours of torque link time in service from the effective date of this AD, or before the accumulation of 750 hours of torque link time in service, whichever occurs later, unless already accomplished in the last 450 hours of torque link time in service. Repetitive inspections are required at intervals not to exceed 500 hours of torque link time in service from last inspection.

To detect cracks adjacent to the 2 1/2" diameter machined boss in any of the four main landing gear torque links (Piper Part No. 65691-00 or 65691-00V) accomplish the following:

(a) Remove paint at least one inch away from the large boss by any suitable means which does not leave a wax residue.

(b) Clean this area for inspection and allow to dry if necessary.

(c) Inspect for cracks by any of the following methods:

(1) Visually with the aid of at least a 10 power magnifying glass.

(2) Fluorescent or dye penetrant inspection.

(3) FAA approved equivalent inspection.

(d) If cracks are present, replace the torque links with serviceable torque links of the same part number before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where installation can be performed.

Piper Service Letter No. 600 pertains to this same subject; however, compliance times must be in accordance with the provisions of this AD.

Operators who have not kept records of hours time in service on individual torque links shall substitute airplane hours time in service in lieu thereof.

Previous AD's 67-20-04 and 70-18-05, concerning main landing gear torque links are still applicable. Piper Kit No. 757-123 as mentioned in these AD's contains appropriate hardware for torque link installation and may be reused.

This amendment becomes effective April 14, 1972.